henderson



18 1927' A. E. HENDERSON AEROPLANE PROJECTILE Ogiginal Filed Jan. 19, 1918 2 Sheets-Smet 1 l,

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A. E. HENDERSON AEROPLANE PROJECTILE 2 Sheets-Sheet 2 Original Filed Jan. 19, 1918 Patented Cet. 18, 1927.

UNITED STATES ALBERT ENNIS HENDERSON, OF'TORONTO, ONTARIO, CANAD..

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Application filed. January 19, 1918, Serial No. 212,618.

The object of the invention is to provide in connection with an aeroplane, designed as4 an offensive, military, or war plane, a means for accurately projecting, discharging, or releasing a bomb, torpedo, or other missile, with reference to a specific objective, and for facilitating the directing or aiming of the projecting means with regard to said objective, illuminating or spotting devices being available for night use, or when the atmosphere is murky, or otherwise laclrs learness.

Further objects and advantages will appear in the course of the following description, it being understood` that changes in forni, proportion, and details of arrangement may be resorted to within the scope of the appended claims Without departing from the spirit of the invention.

In the drawings:

Figure 1 is a side View of an aeroplane provided with an equipment embodying the invention in a preferred form.

Figure 2 is a plan view of the same.

Figure 3 is a front view.

Figure 4 is a detail view in section of the projectile directing and discharging means.

Figure 5 is a view of a sighting device for cooperation with the projecting means.

Figure 6 is a view of a binocular sighting device.

Figure 7 is a view of a convenient form of binocular support.

In the illustrated embodiment of the invention, the supporting vehicle or vessel from which the offensive missile is to be discharged, is represented by an aeroplane of i' which the body portion consists of a fuselage -specifically illustrated herein for the reason that such devices are of common knowledge in this art. Also associated with the main forward sustaining planes are the ailerons 16 which, as in the ordinary practice, are

Renewed March 5, 1927.

adapted for use as lateral balancing means and for securing the lateral tipping or tilting of the structure in curved or spiral flights. In this instance two propellers 17 are illustrated, but it is obvious that this feature may be modied to suit the conditions under which the device is designed to be employed.

Disposed preferably above the center of resistance of the structure, or above and approximately parallel with the axis o-f the fuselage is a series of auxiliary dirigible sustaining planes 18 preferably arranged in two parallel groups one of which is disposed on either side of the vertical plane of the axis of the fuselage and which are adapted for simultaneous deflection from a flat or horizontal plane to afford greater or less sus taining force, or to be arranged at a greater or less incidence so as to modify to a greater or less extent the vertical or lifting com-f ponent of the dynamic resistance. Obviously, however, as may be determined by experiment, or tomeet varying conditions of use, the extent of deflection, or movement from an assumed neutralposition, may be varied as to the respective planes in the series, as for example, the foremost, or the foremost and rearmost planes of the series may be movable simultaneously with the intermediate planes of the series but t0 a greater 'extent and yet be adapted by a corresponding ratio in return movement, to resume the neutral position in conformity with that of the said intermediate planes. Also, as above indicated, these auxiliary sustaining planes are preferably arranged in parallel groups at either side of the vertical plane of the axis of the fuselage, so as to afford an additional stabilizing means, and when this arrangement is adopted the intervening space may be utilized to provide for positioning in the vertical plane of the axis of the fuselage, and also above the horizontal plane thereof of axially vertical drifting planes 19, preferably coupled with actuating means whereby a simultaneous and proportionate adjustment thereof may be secured, either to cause deiiection in one direction or the other from the vertical plane of the axis of the fuselage, or accurate alinement with said plane. The series of drifting planes as well as the series of auxiliary sustaining planes preferably extend approximately throughout the length of the fuselage, at

tion in tdirection' of movement is required. By means of the drifting planes 1t 1s possible to compensate for or neutralize the effect of side winds or drifts of air to adapt the craft to proceed in a direct line toward its objective and' thus avoid the disadvantage incident to heading the craft more or less into the wind, as in the ordinary practice, and thus pursuing a more or less circuitous or indirect route. By means of the auxiliary sustaining planes whereby the elevating or lifting component of resistance may be varied, it is possible to reduce the forward speed of the craft so as to time it more or less accurately with that of a moving objective, such, for example, as a watercraft, submarine, or the like.

Suspended from a point in the fuselage, approximately at the intersection of the longitudinal and transverse axes thereof and adjacent to the center' of gravity is a proj ectile-discharging device 2O which is specifically illustrated in Figure 4, the same being suspended for universal gravital movement so as to permanently maintain an axially vertical posit-ion. To this 'end the easing 2l is provided with a hollow or tubular neck 22, of which the downwardly convexed head 23 is separated by a concave-convex floating web 24 from an upwardly concaved seat 25, anti-friction bearing elements, such as balls 26, being interposed between the surfaces of said parts. Extending through the bore of said neck and anti-frictionally supported, as at 27, upon the head 23 is a spindle 28 having means, such as a pulley 29, through which a rapid revoluble movement may be imparted to the spindle, and provided at its lower endv with a seat 30 for the reception of the head 31 of a projectile 32, preferably provided with external flanges 33 which progress spirally from one end of the body to the other to impart penetrating power and controlled progressive movement to the projectile when traversing a heavier-than-air medium, such as water. The seat 30 is of cage-lilre form and is designed to receive the revoluble movement imparted to the spindle and convey it to the projectile preliminary to `the release of the latter, of which the head is held seated by means of detente or clutching elements 34, normally held in engaging positlons, as by springs. When it is desired to discharge or release the projectile it may bev accomplished by disturbing the relation of the clutching members with the seated head by the depression of a cap 36 actuated by a hand lever 37 or its equivalent, said cap containing a cam ring 38 which is antifrictionally mounted in the cap to avold 1mpedance of the rotary motion oftheclutching member carried by the projectile seat. Said cap is yieldingly sustained b-y means of springs 39, or their equivalent.v

In addition to this projectile-dlscharging or releasing device, the aircraft is preferably provided with sighting apparatus, such as a telescope 40, which may be eitherof the monocnlar type, shown in detail in Figure 5, or of the binocular type, shown in Figure 6, at 4:1. lf of the former type, a universal susjicnding means ft2 may be employed, the same consisting of elements i3 and 4:4, separated by ainifriction devices, so that the telescope is free for gravital movement, and therefore. in a cooperative relation with the projectile-discharging means, to facilitate the aiming of the latter so as to properly and accurately approach the objective, whereas if of the binocular type a similar universal and gravital support of the instrument with the named object in view may be secured by means of a bracket L5 having, for example, a center point (16 disposed between the tubes of the instrument in engagement with a. center socket l? thereon.

Also, as a means of aiding the operator in picking up or locating an object at which a project-ile or missile is to be discharged, an illuminating means 18 may be employed, the same being shown only in a general or diagrammatic way in the drawing, but being designed for universal or gravital suspension so as to cooperate accurately with the projectile-discliarging and sighting means and may, through any available agency, be of suoli power as to penetrate the atmosphere, and also a denser medium, if required, even though the former maybe obstructed. more or less by moisture or smoke. Under any condition, however, the projectileedischarg ing, sightingand illuminating means should be suspended from the craft under such conditions as to cooperate accurately and be directed without the intervention of the operator along a common path or toward a common objective, so that the operator may be enabled to readily see an object to be attached and discharge the projectile at the right moment and under conditions most favorable for the purpose in. View. Obviously, the accuracy with which this object may be carried out is vastly increased by reason of the control of the craft which is afforded to the operator by such an arrangement of elements as described hereinbefore, and more particularly by reason of the means suggested for permitting the velocity or progress of the craft to be reduced to a minimum while maintaining such an elevation, for example, above the surface of the water in which a submarine may be located, as to enable the projectile to acquire the necterminacion.

-essa-ry velocity by gravity before encountering the water, to the end that a suliiciently accurate and rapid progress of the projectile through the water may be attained.

As illustrative, merely, of means for adjusting the auxiliary sustaining and lateraldrift planes, there are shown, in connection with the horizontal axes or shafts 60 of the former (suitable braces 59 being extended to their outer ends) the worms 6l on the longitudinal shaft 62, meshing with worm gears G3 on the shafts GO, while the verti cal shafts 64 of the planes 19 carry Wormgears 65 with which mesh worms 6G on the operating shaft 67. Also, guys or braces 59 may be extended to the upper ends of tne spindles 64 of the vertical drift planes.

While in the drawings no specific means has been illustrated for imparting revoluble movement to the pulley 29 and hence to the projectile seat, any mechanical contrivance of known capabilities from a hand crank to a high speed motor, utilizingany available motive agency may be employed in this connection, without in any way modifying the purpose or eliiciency of the elements herein described which constitute factors of the suspending, directing, revolving and delivering of the projectile under conditions which carry out the indicated objects of this invention.

Having described the invention, what is claimed is:

1. An aeroplane having propelling and guiding means a projectile discharging means gravitally suspended for universal movement adjacent to the center of gravity of the structure, and means for imparting revoluble or gyratory movement to the projectile.

2. An aeroplane having propelling and guiding means, a projectile discharging means gravitally suspended for universal movement from a point near the axis and the center of gravity of the structure, and means for revolving the discharging means to impart revoluble or gyratory movement to the projectile.

3. The combination with a `carrying vessel of a gravitally suspended projectile-seating means comprising a rotatable seat, independent devices for engaging and holding a projectile therein and means for simultaneously releasing said devices, substantiallyas set forth.

4. The combination with a carrying vessel of a gravitally suspended revoluble projecn tile seating means, and clamping devices for engaging a seated projectile to communicate the rotative movement of the seat thereto.

5. The combination with a carrying vessel of a gravitally and universally suspended casing, a yrotative projectile seat antifrictionally mounted relatively to said casing, and releasable projectile-holding means for antifrictionally mounted element for contact with said engaging means, to elfect the release of the latter to permit the discharge of the projectile.

7. ln. a device of the character described an aeroplane capable of being controlled in regard to its vertical and horizontal movements without materially interfering with the horizontal position of the plane, a universally gravitally suspended casing on the 'f' aeroplane, an antifrictionally supported rotatable bomb supporting means in the chamber, means for rotating said. means, and antifrictional releasing means for the bomb, substantially as set forth.

8. A device of the character described comprising an aeroplane having a gravitally suspended antifrictionally supported chamlier. an antifrictionall mounted bomb su i- V porting device within the said chamber having inwardly projecting jaws adapted to engage the upper iianged endl of the bomb, means for rotating the said supporting device and the bomb carried thereby, and a releasing device adapted to disengage the jaws without retarding the rotation of the bomb, substantially as set forth. l

9. In an aeroplane, a gravitally suspended antifrictionally mounted chamber, a bomb supporting device centrally supported in the said chamber, jaws to engage a flange on the bomb, means for rotating said bomb, antid frictional releasing means, and co-acting sighting devices carried by the plane.

10. In an aeroplane, a 'gravitally suspended chamber, a bomb supporting device, means for imparting rotation to the said device, and antifrictional releasing means connected with the said chamber, substantially as set forth.

1l. An aeroplane bomb having spiral flanges along its downwardly projecting body, a flanged shoulder at its upper end, supporting means adapted to engage the said iiange said supporting means being rotatably mount-ed in a gravitally suspended chamber carried by an aeroplane or other sustaining device, and means for imparting rotation to the said bomb before being released, substantially as set forth.

12. Gravitally suspended antifrictionally mounted bomb supporting means carried by an aeroplane or airship, and means for imparting rotation to a bomb carried thereby, substantially as set forth.

I flanges, means for supporting and rotating the same, said means being journalled vertically within a gravitally suspended antifrictionally mounted chamber, and an antifrictional releasing device for the bomb carried by an aeroplane or the like, substantially as set lforth.

15. A gravitally suspended antifrictionally supported chamber carried by an aeroplane, a bomb su porting device vertically journalled withlnthe said chamber having supporting jaws, an antifriction lreleasing means for the said jaws, and means for imparting rotation to the said supporting device and bomb before the release ofl the bomb, substantially as set forth.

16. A bomb for aeroplanes havingspiral anges on its downwardly projecting portion, a shoulder on its upper extremity, a row tatable Asupportino device engaging said shoulder, said device being antfrictionally p mounted in a gravitally suspended universally movable chamber carried by an aeroplane or the like, substantially asset forth.

17. For use with an aeroplane projectile having progressive spiral flanges on the body thereof and a radial shoulder at the upper end, supporting means adapted to engage the said shoulder, said means belng vertically and antifrictionally journalled within a chamber gravitally suspended from the center o'E 'gravity of an aeroplane, means for imparting rotation to the projectile and its supporting means before the projectile is released, and antifrictional releaslng means carried by the said chamber, substantially as set forth.

18. In combination, projectile discharging means suspended for pivoted movement, means for rotating said discharging means and the projectiles therein about a vertical axis, and means to discharge such projectile without interfering vwith their rotation, substantially as set forth.

19. In combination, projectile discharging means suspended for pivoted movement, means for rotating said discharging means and the projectiles therein about a vertical axis, and means to discharge such projectile, substantially as set forth.

In testimony whereof I have hereunto signed my name.

ALBERT ENNIS HENDERSON. 

